Releasable tank and bomb rack



Feb. 9, 1937.

R. D. CARLE TON ET AL RELEASABLE TANK AND BOMB RACK Filed Feb. 21, 19354 Sheets-Sheet l ggffm INVENTORJ' RHLPIID (HELL-M9! (IBM mac 1937. R. n.CARLETON El AL 2,069,996

RELEASABLE TANK AND BOMB RACK Filed Feb. 21, 1935 4 Sheets-Sheet 2 Feb.9, 1937. R. D. CARLETON m AL 2,069,995

RELEASABLE TANK AND BOMB RACK 4 Sheets-Sheet 3 Wm o a g E... 7 8 w a 90r m i o J 19 4 nr l Q nn H 1 a a M .Z c 0O 5 a E 7 E /O 1 r o 6 ,H O 1 V.2 a a I w 3 2 I W W @u I W m AW. l a 2 a D 1 2 m Q\\ P ah I w T. W0 W1p f T a f N b. v Q 0 8 n/ 7 1 2 Z a X F a o, m 0 L 2 R. p. CARLETON ETAL RELEASABLE TANK AND HOME RACK Feb. 9, 1937.

Filed Feb. 21, 1935 4 Sheets-Sheet 4 IN V EN TORJ RHLPI! Z CHRLETOH'"'4' (LEM 6 ATTO Patented Feb. 9, 1937 RELEASABLE TANK AND BOMB RACKRalph D. Carleton, Snyder, and Clem G. Trimbach, Eggertsville, N. Y.,assignors to Our-tiss- Wright Corporation, a corporation of New YorkApplication February 21, 1935, Serial No. 7,476

5 Claims This invention relates to aircraft, and is particularlyconcerned with mounting arrangements for fuel tanks and armament, suchas bombs.

Although the invention may be used in any 5 type of aircraft, it isparticularly adapted for military craft of the ground attack type, whichare usually of two-place capacity and in which it is necessary for thepilot to be placed as far forward as possible in order that he may have10 maximum visibility, and in order that he may be able to look directlydown over the side of the fuselage without interference from the leadingedge of the wing. This type of aircraft also carries a gunner occupyinga rearward cockpit. In 15 the conventional type of craft it has .beencustomary to place the fuel tanks forward of the pilot and directlybehind theengine, but this location interferes with forward placement ofthe gunner and also, since it is necessary, in case of 2 forced landing,to rid the ship of hazardous equipment such as bombs, fuel tanks and thelike. If the tanks were located forwardly of the center of gravity, thebalance of the aircraft would be seriously upset should they be released25 when nearly full. Thus, it is contemplated in this invention, tolocate the main fuel tank substantially coincidental with the center ofgravity of the airplane with part of the crew ahead thereof, and toprovide means by which the fuel tank 30 may be dropped clear of the shipin case of emergency. Since craft of this type are adapted to carryadditional equipment in the form of bombs, or extra fuel supply, orsmoke-producing equipment, we find it convenient to suspend this alter-55 native auxiliary equipment below the main fuel tank and to the samepart of the structure which holds the main fuel tank. Thus, in anemergency, dropping of the main fuel tank simultaneously drops theauxiliary equipment which is 40 bound to be hazardous in case of forcedlanding, and also, the extra equipment, which varies in weight fordifferent forms thereof, is located .directly below the center ofgravity.

A primary object of this invention is to pro- 45 vide means forsupporting the main fuel tank and an auxiliary fuel tank, or bombs, orsmoke tanks, in such a manner that they may be released.

Another obj ect provide means for breaking 50 all connections betweenthe tanks and auxiliary equipment so that the parts such as fuel lines,bomb controls and the like may not be severed or turn asunder under theinfluence of dropping of the equipment;

5 Another object is to provide a tank and auxiliary equipment supportwhich may be completely assembled to the main tank, after which thewhole unit may be installed in the aircraft.

A further object is to provide a standard form of tank cradle which maybe attached to the 5 aircraft fuselage, whichcradle may be made up onthe ground, alternatively, with bomb equipment, extra tank equipment, orsmoke apparatus.

Further objects will become apparent in reading the subjoinedspecification and claims, and from an examination of the drawings, inwhich similar numbers indicate similar parts, and in which:

Fig. l is a side elevation of part of an aircraft fuselage, showingprincipally in dotted lines, the releasable main fuel tank inside thefuselage, and showing an auxiliary streamlined belly tank carried by themain tank supporting mechanism;

Fig. 2 is a side elevation, generally similar to Fig.- 1, but indicatingthe attachment of a plu- 'rality of bombs in place 'of the streamlinedbelly tank;

Fig. 3 is an enlarged side elevation in detail, showing the tanksupporting mechanism, an auxiliary belly tank attached thereto, and thebreakable fuel connections associated with said tanks;

Fig. 4 is an enlarged side elevation of the breakable fuel. connection;

Fig. 5 is an end elevation of the breakable fuel connection;

Fig. 6 is a front elevation of the releasable main tank supportingcradle having an auxiliary belly tank associated therewith;

Fig. 7 is an end elevation similar to Fig. 7, showing the alternativeattachment of bombs to the main tank cradle; and

Fig. 8 is a side elevation, generally similar to Fig. 3, showing theattachment of bombs in place of the auxiliary belly fuel tank.

The aircraft Ill includes a fuselage ll having a forward cockpit l2 anda rearward cockpit l3 with a space H provided between the cockpits forthe accommodation of a main fuel tank l5. Said tank is strapped toacradle l6, which is releasably mounted in the fuselage structure I1, 5the cradle being provided with mechanism therebelow for the support ofan auxiliary streamlined fuel tank |8 which lies below the fuselage andin the airstream. The cradle I6 is also arranged so that the fuel tankl8 may be removed therefrom and conventional bomb racks l9 may beattached thereto for the support of bombs 20. Although not shown, anyother form of auxiliary equipment may be attached below the cradle l6,such as smoke-producing tanks or the pended auxiliary equipment, isshown at 2|, this means including a pull handle 22 to which a cable 23is attached for the breaking of the fuel connection 24, and to which acable 25 is attached for releasing the cradle l6 with its attachedequipment. The same form of releasing means 2| is included when bombsare carried, as in Fig. 2, but when bombs are carried, separate bombreleasing means 26 are installed so that any one of the bombs 29 may bereleased at will from the cradle l6, without dropping the cradle. D

Now referring to Figs. 3 and 6, the cradle l6 comprises transversetrusses 21 joined by longitudinals 28, each truss 21 having laterallyextending studs 29. for engagement within slots 36 formed in fittings 3|carried by the longerons of the fuselage structure l1. To each fitting3| a dog 32 is pivoted, which dog may swing upwardly to hold the stud 29within its slot 30., A

sear 33 is also pivoted to the fitting, said sear having a notch withinwhich the free end of each dog 32 may engage, upon which engages mentthe cradle I6 is firmly but releasably held to the fuselage. The severalsears 33 are joined by longitudinal trigger bars 34 at the forward endsof which are pivoted bell cranks 35, one end of each of which is notchedto engage a catch 36 fixed to the forward fitting 3|. The cradlereleasing cable 25 is shackled to the opposite end of the bell crank 35.By a sharp pull on the cable 25, the bell crank is released from thecatch 36, and further pulling of the cable 25 pulls the trigger bar 34forwardly, carrying with it the sears 33 and disengaging said sears fromthe dogs 32 to permit release of the cradle l6.

It will be noted that the main fuel tank l5 rests upon the cradle l6,and is fixedly clamped thereto by straps 31 terminating in fittings 38fixed to end portions of the cradle.

Figs. 3, 4, 5, and 6 show the fuel conduits from the gas tank l5extending forwardly through the breakable connection 24 to an engine(not shown) to be supplied with fuel. As shown, two conduits 39 and 46extend to the main fuel tank, the conduit 49 extending well up into thetank as at 4| to provide a normal service fuel capacity, while theconduit 39 extends only a short distance within the tank, as at 42, toprovide a reserve supply. Suitable valve switching means. well known inthe art, are provided by which the pilot may switch from service supplyto reserve supply should he run short of fuel.

Both of the conduits 39 and 4|! extend to a fitting 43, of the breakableconnection 24, having a biased forward face 44 engageable with asimilarly biased face 45 of a fitting 46, said fitting being fixedlyattached to the aircraft as by a. bracket 41. From the fitting 46, fixedfuel conduits 48 and 49 extend forwardly to the engine. The biased faces44 and 45 of the fittings 43 and 46 are held in engagement with oneanother by means of hooks 50 pivoted to the fitting 46 and extendingdownwardly and rearwardly to hook around a transverse tube 5| adjustablyattached to the fitting 43 by means of screws 52. On assembly of theseparable fuel connection, the screws 5| are loosened and the faces 43and 45 placed in engagement. Thereupon, the hooks 50 are engaged aroundthe tube 5| and the screws 52 are tightened to effect a leaf-proof jointin the assembly. Release levers 53 are pivoted at 54 toward the ends ofthe hooks 50, said release like.- In Fig. 1,- the operating means forreleasing the cradle l6,- with the tank l5 and sus-' levers having camportions 55 resting against the ends of the tube 5|. The levers 53 arejoined to the fuel valve release cable 23. Upon pulling said cable 23,the levers 53 are rocked on their assembly may drop clear of theaircraft without destroying the fixed portions of the fuel conduitsystem.

The belly tank l8, shown in Figs. 3 and 6, may be semi-permanentlyattached at its rearward end to the cradle l6 by means of fittings andstruts generally designated as 56. The forward end of the tank I 8carries struts 51 having forwardly opening slots 56 within which an eye59 of a. bracket 60 engages, said bracket being fixed to the aircraft.When the cradle I6 is released, the rearward end of the tank l8 movestherewith, whereupon the strut 51 disengages the bracket 60 and the tankl8 may drop clear with the cradle and main fuel tank l5. As shown, afuel conduit 6| from the auxiliary tank I, extends upwardly andforwardly to the main fuel control valve (not shown) and this conduit 6|may obviously be provided with a separable fuel connection such as 24,or with some equivalent device.

Smoke. tanks, when used, may beattached to the cradle l6 and to thefuselage in substantially thesame manner as provided for the auxiliaryfuel tank l8.

Referring now to Figs. 7 and 8, we show the alternative installation ofa plurality of bombs on the cradle l6. Here, the elements 56 areremoved, and in place thereof, several bomb racks 62 are attacheddirectly to the longitudinal tubes 28 of the cradle |6.. These bombracks in themselves form no part of the invention, and are of acharacter well known in the art. Push-pull tubes 63 extend forwardlyfrom each bomb rack to levers 64 pivoted at 65 to the aircraftstructure. The joints between the levers 64 and the tubes 63 are suchthat, when the cradle I6 is released from the aircraft, the bombs, bombrack 62 and cradle |6 all drop free, while the levers 64 remain intactwith the aircraft. Such joints, indicated at 66, comprise a verticallyslippable connection by which fore and aft movement of the levers 64operates the push-pull tubes 63, but when the cradle it with itsequipment falls clear, a light shear pin 61 breaks to allow freeseparation between the elements of the joint.

In Fig. '7 is shown the bomb suspension apparatus, and struts 68 arefitted to the cradle truss to steady the bombs from lateral oscillationwhile the craft is in flight. Certain of these struts, such as 6.9, areadjustable by a nut 10', to permit of facile mounting of the bombs. Whenmounting the bombs, the struts 69 are shortened and the bombs suspendedfrom their respective racks 62. Thereupon, the struts 68 are put inplace, the struts 69 are-put in place, and the latter struts are thenlengthened to firmly hold the bombs in position. Releasing of any one ofthe bomb racks 62 permits its respective bomb to drop clear withoutinterference and without likelihood of interference with any other partof the aircraft. v

The bomb release levers 64 are suitably connected to the bomb releasehandle organization '26 in the pilot's cockpit.

Generally summarizing the mechanism as a whole, it will be seen that thecradle i6 is releasably held at its four corners to the fuselage of theaircraft. The main fuel tank, mounted on the cradle, and any auxiliaryapparatus carried below the cradle, are simultaneously releasable byoperating the handle 22, this maneuver generally being accomplished incase of the necessity for a forced landing when it is desired to rid thecraft of hazardous components thereof. In normal military operation, onephase involves bombing missions and the mechanism heretofore described,permits of the normal dropping-of bombs individually. In other types ofmissions, as for long distance observation or ground strafing or thelike, when a greater supply of fuel is carried, or when it is desired toproduce a smoke screen,

the bombs are replaced by fuel tanks or smoke tanks which are relativelynon-expendible and which would only be dropped, along with the eradle i6and the main fuel tank, in case of emergency.

While we have described our invention in detail in its present preferredembodiment, it will be obvious to those skilledin the art, afterunderstanding our invention, that various changes and modifications maybe made therein without departing from the spirit or scope thereof. Weaim in the appended claims to cover all such modifications and changes.

What is claimed is:

1. In aircraft having'a fuselage, a cradle re-.

means for selectively releasing said apparatus only from said cradle.

2. A demountable assembly for an aircraft fuselage comprising a cradle,a fuel tank mounted on and above said cradle for normally occupying aportion of said fuselage, auxiliary apparatus suspended below andreleasably attached to said cradle, means for selectively releasing saidapparatus from said cradle, and means selectively operable to releasesaid cradle, with said tank and apparatus, from said fuselage.

3. In aircraft, in combination, a bomb rack for a plurality of bombs,means for selectively releasing individual racked bombs, means forselectively releasing the rack and bombs as a unit, and a tank carriedby and above said rack and releasable therewith.

4. In aircraft havinga releasable fuel tank, a

cradle by which said tank is carried and having lugs extendingtherefrom, fittings on said aircraft having downwardly opening slotswithin one of which each said lug is engageable, a dog pivoted to saidfitting for holding said lug within said slot, a scar engageable withsaid dog for holding the latter in lug-retaining position, and a triggerbar connected to a plurality of said sears for simultaneously releasingall lugs from their respective fittings.

5. In an aircraft fuselage, a fuel tank normally lying therewithin, acradle on which said tank is mounted, means for releasably attachingsaid cradle, at a plurality of points, to said fuselage, a belly'tanksecured atone end to said'cradle and a slip joint connecting the otherend of said belly tank to said fuselage, said slip joint beingreleasable upon dropping away of said cradle and maintank from saidfuselage.

RALPH D. CABLETON.

CLEM G. 'I'RIlldBACH.

